Auxiliary propeller for airplanes



y 1946' JJERNEST 2,403,353

' AUXILIARY PROPELLER FOR AIRPLANES 4 Filed Dec. 11, 1943 v 2Sheets-Sheet l IN VEN TOR.

ATTORN Y fibres Ewes! July 2, \1946. I J. ERNEST 2,403,353

AUXILIARY PROPELLER FOR AIRPLANES Filed Dec. 11, 1943 2 Sheets-Sheet 2INVENTOR. 7,895 E'ZGSZ A TTORNEY Patented July 2, 1 946 UNITED STATESPATENT OFFICE AUXILIARY PROPELLER FOR AIRPLANES James Ernest, New York,N. Y.

Application December 11, 1943, Serial No. 513,836

1 Claim. 1

This invention relates to new and useful improvements in a diversepropeller for airplanes.

More specifically, the invention proposes the construction of a newdiverse and revolutionary propeller for airplanes characterized by amotor for driving the propeller turnably supported upon a pair ofstandards mounted on the bottom of the fuselage in line with the mainwings, and arranged in a manner to be directed forwards to change theforward thrust of the plane.

A further object of the invention proposes the provision of a means forturning the motor about its pivots to direct the propeller downwards toa take-off or landing position, or rearwards at an angle to increase thefront thrust and speed of the airplane and for rapid climbing.

It is a further object of this invention to create precise and constantvacuums where it is needed and to counteract gravity and air resistance.

Another object of the invention proposes the provision of a means forcausing the motor casin to be turned at different speeds and angles atthe discretion of the pilot.

Still another object of the invention proposes the provision of meansfor supplying gasoline to the motor in all of its turned positions.

For further comprehension of the invention, and of the objects andadvantages thereof, reference will be had to the following descriptionand accompanying drawings, and to the appended claims in which thevarious novel features of the invention are more particularly set forth.

In the accompanying drawings forming a material part of this disclosure:

Fig. 1 is a side elevational view of an airplane provided with anauxiliary propeller means in accordance with this invention.

Fig. 2 is a similar view to Fig. 1, but illustratin the auxiliarypropeller in a different position.

Fig. 3 is another view, similar to Fig. 1, but illustrating stillanother position of the auxiliary propeller.

Fig. 4 is an enlarged vertical sectional view taken on the line 4-4 ofFig. 1.

Fig. 5 is a vertical sectional view taken on the line 5-5 of Fig. 4.

Fig. 6 is an enlarged horizontal sectional view taken on the line 6-6 ofFig. 4.

Fig. '7 is a vertical sectional view taken on the line 1-1 of Fig. 4.

Fig. 8 is a fragmentary view looking in the direction 88 of Fi 4.

The auxiliary propeller for airplanes, according to this invention, isused in combination with an airplane I0 having a fuselage I I providedwith 2 main wings I2 which extend laterally from the sides of thefuselage I I. The front of the fuselage II is provided with the usualmotor driven propeller [3.

A pair of standards It made of any suitable material and shape ismounted on the bottom of the fuselage II in line with the main wings l2and rotatively supports a solid shaft I5, A tubular shaft I6 is slidablybut non-rotatively mounted on the solid shaft I5 and carries a casingI'I enclosing a motor for driving a propeller I8 in an oppositedirection to the main propeller. The propeller I8 may be of any standardtwo or three blade type. The tubular shaft I6 is provided with aninwardly extending tongue I9 which engages a complementary groove 20formed in the solid shaft I5 for accomplishing the slidable butnon-rotative mounting of the tubular shaft It on the solid shaft I5.

A pair of opposed beveled gears 2i of different diameters are mountedupon one end of the tubular shaft I5. As shown in Fig. 4, the beveledgears 2| are positioned between a pair of adjacent beveled gears 22which are fixed upon stud shafts 23. The stud shafts 23 are rotativelysupported in a bracket 24 which extends from the inner face of one ofthe standards Ii. Flexible drive shafts 25 extend from the stud shafts23 and are projected into the fuselage II to be connected With a drivemeans for rotating the beveled gears 22 when desired. The means fordriving the flexible shafts 25 is not illustrated on the drawing, andmight be an automatic drive provided with an electric motor, or might bea drive terminating in a crank adapted to be manually turned.

Means is provided for shifting the tubular shaft I6 on the solid shaftI5 for engaging the first beveled gears 2i with its respective drivengear 22. This means comprises a pivotally supported lever 26 whichextends from the interior of the fuselage I I and is provided at itsbottom end with a forked portion 21 having inwardly extending trunnionpins 28. The pins 28 engage a groove 29 formed in a collar 30. Thecollar 39 is fixedly mounted on the tubular shaft I6 and pivoting thehandle 26 results in the tubular shaft being shifted with relation tothe solid shaft I5.

Since the beveled gears 2I are of different diameters their selectiveengagement with the driven gears 22 will cause the motor casing H to beturned at different speeds, depending upon which gear 2I is inoperation.

A means is provided for limiting rotation of the shafts I5 and Hi to aposition in which the propeller will be directed forwards or to aposition in which the propeller will be directed rearwards and downwardsat an angle. This means comprises a stop 3| formed on the solid shaft I5and which operates between spaced stops 32 formed on the adjacent faceof one of the brackets I4. This end of the solid shaft i5 is formed withan inwardly extended opening 33 and has a gasoline feed line 34rotatively con-- nected therewith at a junction 35. Gasoline supplied bysaid line 34 will be carried to the motor within the casing [7 by theopening 33 extended in from the end of the solid shaft IS. The rotativeconnection between the gasoline feed line 34 and the solid shaft I5permits the solid shaft to be turned relative to the said line 34.

A suitable heat insulating hood 35 .is provided with a slot 36 for thepropeller shaft forkeeping the auxiliary device from freezing.

The operation of the device is as follows:

The control lever 2t and the mechanism for driving the flexible shafts25 will be located within the fuselage ll of the airplane ltl withinreach of the pilot, permitting him to shift the lever 25 to-engageeither of the driven gears '22 g with its respective beveled gear 2|.

The means for driving the flexible shafts 25 is then brought intooperation to turn the beveled gears 2| and turn the shafts l5 and itthrough the medium of the gears 2 I. This will rotate the casing ii andchange the angular position of the propeller 8 with relation to "theairplane 511. If the propeller is directed forwards, as illustrated infull lines in Fig. l, it-will change the forward speed of the plane. InFig. 3, the propeller i8 is shown in a rearward position to increase theforward thrust of the plane and increase its forward speed'through theair and simultaneously help the plane to climb more rapidly towards highaltitudes. The propeller might be directed downwards, as indicated bythe dot and dash lines It in Fig. l, and in the full lines in Fig. 2. Inthis position the propeller it will producean upward thrust, increasingthe lift of the airplane-causing it to take off more nearly verticallywith a greater load.

In this device whenthe engine is made to face in the downward directionby the pilot as-shown in Fig. 2, the plane will take off in coordinationWit/b13116 front propeller. It will also land when the propellers willbe in the same relative position.

When the engine is made to face toward the back as shown in Fig. 3, thespeed and the thrust of the plane will be increased and willsimultaneously help the plane to climb more rapidly towards highaltitude.

The illustration in Fig. 1 shows the two propellers in aligned positionsbut the propellers are being rotated in opposing directions, to changethe speed of the airplane.

It is to be understood that this propeller arrangement may be used forboth fighting and commercial. type of planes with the followingadvantages:

1. The airplane will take off and land more nearly vertically.

2. It will climb more rapidly.

3. It willconsiderably increase the speed of the airplaneand will have alonger range.

4.'It will considerably increase the cargo capacity of the airplane.

5. By means of this arrangement the lives of the crew willbecome safer.

While I have illustrated anddescribed the-preferred embodiments of 'myinvention, it is -to be understood that I do not limit myself to theprecise constructions herein disclosed and the right is res rved to allchanges and modifications coming-within the scope of the invention asdefined in the appended'claim.

Having thus described my invention, what I claim as new, and desire tosecure by United States Letters Patentis:

An airplane having a pair of spaced brackets rotatively supportinga'first shaft upon which a motor driven propellor unit is turnablysupported, means for turning said unit'in one direction or the other atdiiferentrates of speed, comprising a tubular shaft slidably butnon-rotatively mounted on said first mentioned shaft, a pair of spaceddriven bevel gears positioned adjacent one end of said tubular shaft, apair of opposedbevel gears of different diameters mounted on theend'ef-said tubular shaft between said spaced driven bevel gears, meansfor moving said tubular shaft on said first mentionedshaft one way orthe other for selectively engaging either of said opposed bevel gearswith its respective gear of said pair of spaced driven bevel gears andmeans'carried by said first mentioned shaft for supplying fuel to saidmotor.

JAMES ERNEST.

